基于二次流控制规律的非轴对称端壁造型优化设计

尤付浩; 李相君; 鲁庆; 崔义强; 朱政宇

doi:10.13224/j.cnki.jasp.20220215

基于二次流控制规律的非轴对称端壁造型优化设计

doi: 10.13224/j.cnki.jasp.20220215

大连海事大学船舶与海洋工程学院，辽宁大连 116026

基金项目: 国家自然科学基金青年项目（51906027）；辽宁省博士科研启动基金计划项目（2019-BS-027）

详细信息

作者简介:
尤付浩（1995-），男，硕士生，主要从事叶轮机械气动热力学研究。E-mail：fhyou@dlmu.edu.cn

通讯作者:
李相君(1989-)，男，副教授、硕士生导师，博士，主要从事叶轮机械气动热力学研究。E-mail：xjli@dlmu.edu.cn

中图分类号: V231.3
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出版历程
- 收稿日期: 2022-04-15
- 网络出版日期: 2023-04-19

Non-axisymmetric endwall based on secondary flow control law modeling optimization design

Naval Architecture and Ocean Engineering College， Dalian Maritime University，Dalian Liaoning 116026，China

摘要

摘要:
针对高负荷轴流压气机端壁角区分离问题，提出了一种多局部控制端壁二次流、适用于多工况的端壁造型方法，在选取参数的同时考虑结合优化，通过少量参数来控制型面变化。该方法的思想是定义对端壁二次流有不同影响的表面单元，然后通过几何叠加的方式将它们的影响组合起来。而后将该方法应用到多目标优化设计中。优化结果表明：高负荷叶栅的总压损失系数在设计点降低0.03，大攻角点降低0.05时，与传统方法相比，新方法的优化设计过程收敛更快，计算时间更短。最优造型设计规律是在叶片通道内构造一个吸力侧上升、压力侧下沉的端壁面，同时局部抬高吸力面角区，前缘至凸起部位上坡平缓。流场分析表明，该方法在控制变量较少的情况下，对端壁几何形状产生了清晰直观的影响。同时有效结合表面单元在二次流控制中的作用，抑制角区分离。由此可见，新开发的端壁造型优化设计方法与以往的研究相比具有一定的优势。
- 角区分离 /
- 端壁造型 /
- 流动控制 /
- 优化设计 /
- 压气机
Abstract:
To deal with corner separation in high-load axial compressors, a new endwall contouring method for controlling the endwall second flow in more than one local area, generating the geometry with fewer control variables, and adapting to multiple working conditions was proposed. According to the idea of the new method, surface units with different effects on endwall secondary flow were defined, then their effects were combined by superimposing their geometry. Then the method was applied to multi-objective optimization design, The optimization results showed that the total pressure loss coefficient of the high-load cascade was reduced by 0.03 at the design point and 0.05 at the increased incidence. Compared with the traditional method, the optimization design process of the new method converged faster and the calculation time was shorter. As per the most effective design rules, an endwall surface with the rising suction side and sinking pressure side in the blade channel was constructed while locally raising the suction surface corner with a gentle upstream slope. The flow field analysis showed the new method achieved a clear and intuitive influence on the endwall geometry with fewer control variables. Also, it effectively combined the functions of the surface units in secondary flow control to suppress the corner separation. It thus indicates the advantages of the newly developed endwall contouring method compared with previous studies.
- corner separation /
- end wall contouring /
- flow control /
- optimization design /
- compressor

HTML

图 1 造型单元面的加权叠合

Figure 1. Weighted superposition of the end wall contouring units

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图 2 全局单元定义及流场作用情况

Figure 2. Definition of the full-area unit and its effects on the end wall flow field

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图 3 局部单元定义及流场作用情况

Figure 3. Definition of the localized unit and its effects on the end wall flow field

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图 4 不同权重下的标准空间内造型结果对比

Figure 4. Influence of the weight factor on the variation of the end wall contouring

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图 5 端壁造型由标准空间向压气机端壁空间映射

Figure 5. Mapping from the standard space to the end wall region of a compressor passage

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图 6 叶栅几何参数示意图

Figure 6. Parameters definition of the cascade diagram

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图 7 网格示意图

Figure 7. Sketch of mesh

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图 8 尾缘下游0.5C位置总压损失系数沿叶高分布

Figure 8. Spanwise distribution of ω at 0.5C downstream of the trailing edge

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图 9 实验与计算壁面静压系数分布对比

Figure 9. Experimental and CFD result comparison of the static pressure coefficient on the end wall surface

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图 10 优化设计流程

Figure 10. Processing of the optimization design

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图 11 造型变量与总压损失系数的相关性分析

Figure 11. Correlation analysis between control variables and total pressure loss

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图 12 造型结果的总压损失分布

Figure 12. Total pressure loss of profiling cases

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图 13 优化造型结果高度云图（Case2）

Figure 13. Height contours of the optimized model （Case2）

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图 14 尾缘下游0.5C处总压损失系数、轴向密流比与出口气流角分布

Figure 14. Spanwise distribution of total pressure loss coefficient，AVDR and out flow angles at 0.5C downstream of the TE

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图 15 损失源所在区域划分

Figure 15. Integral region of the loss sources

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图 16 应用非轴对称端壁造型前后总压损失增长速率沿轴向分布

Figure 16. Streamwise distribution of growth rate of total pressure loss before and after applying NEWC

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图 17 应用非轴对称端壁造型前后的三维流场

Figure 17. Three-dimensional flow field before and after applying the NEWC

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图 18 OP2应用非轴对称端壁造型前后三维流场比较（i = 4°）

Figure 18. Comparison of three-dimensional flow field before and after applying the NEWC at OP2 （i = 4°）

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图 19 OP1处应用非轴对称端壁造型前后三维流场比较（i = 0°）

Figure 19. Comparison of three-dimensional flow field before and after applying the NEWC at OP1 (i = 0°)

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图 20 OP3处应用非轴对称端壁造型前后三维流场比较（i = −2°）

Figure 20. Comparison of three-dimensional flow field before and after applying the NEWC at OP3 (i = −2°)

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表 1 原型叶栅几何参数与气动参数

Table 1. Geometry parameters and aerodynamic parameters of the original cascade

参数	数值
叶高h/mm	100
弦长C/mm	40
轴向弦长C_a/mm	36.2
叶距s/mm	20
进口马赫数Ma	0.6
进口几何角β_1k/（º）	25
出口几何角β_2k/（º）	80
安装角γ/（º）	64.85
设计攻角i/（º）	0

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表 2 叶栅通道损失源分布

Table 2. Loss sources of the cascade

i/（°）	L_LE	L_bf	L_su	L_sd	$L_{S_{ {\rm{ke} } } }$	L_sep
0	0.0744	0.0631	0.0418	0.0566	0.0017	0.0968
4	0.1065	0.0755	0.0561	0.0852	0.0025	0.1389
−2	0.0853	0.0685	0.0466	0.0452	0.0011	0.0907

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表 3 端壁造型对损失源作用

Table 3. Effect of NEWC on the loss sources

i/（°）	$（{L_{ {\text{sep,Case2} } } }{ { - } }{L_{ {\text{sep,Baseline} } } }）$/ ${\displaystyle\sum L _{ {\text{Baseline} } } }$/%	$（{L_{ {\text{Case2} } } }{{ - } }{L_{ {\text{Baseline} } } }）$/ ${\displaystyle\sum L _{ {\text{Baseline} } } }$/%
0	−10.18	−12.89
4	−13.01	−16
−2	−6.38	−7.98

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